Computational Aerodynamic Investigations on Wash Out Twist Morphing MAV Wings

This paper presents detailed mathematical modeling, controller design, and flight test results for the autonomous mission of a nonconventional fixed-wing biplane micro air vehicle (MAV) called Skylark having span and chord length within 150 mm. Although numerous fixed-wing MAV designs are reported in the open literature, an MAV’s reliable autonomous flight is still a challenge. The primary difficulties in performing the autonomous mission of fixed-wing MAV are system integration within the weight and power budget, center of gravity (CG) management, and flight controller design for fast dynamics. In this paper, the key challenges are addressed by using the higher payload capacity of Skylark, suitable selection and design of avionics components, and design of controller after detailed development of the mathematical model, including the additional effect of propeller wash and motor countertorque. An autonomous flight test is successfully demonstrated after the validation of algorithms and software architecture through nonlinear six-degrees-of-freedom simulation. The detailed design and development approach will increase the MAV’s performance and reliability in civil and military applications. 

Autonomous Flight Test of a Novel Nonconventional Biplane Micro Air Vehicle

It is challenging to control a UAV during the actuator failure because it is a highly nonlinear, coupled, underactuated system. Partial UAV control is achievable by reallocating the control signals, but control over one state has to be compromised, which would be the yaw angle for the quadrotor UAVs. 

Deflecting Surface-Based Total Rotor Failure Compensation for Biplane Quadrotor

Air Classification of Crushed Materials

Unmanned aerial vehicles (UAVs) are applied in many civil and military operation areas due to their availability and cost-efficient operational capabilities. The take-off and landing methods chosen for an aircraft depend on its operational design requirements. There are various types of UAV configurations under the main groups of fixed wings, rotary wings, and hybrid categories. These different configurations offer specific operational and technical advantages that make each configuration unique for the aimed application. In this chapter, landing gear configurations of fixed wing, rotary wing, and hybrid UAVs were assessed. The components and design selections were evaluated. The rule of right thumb design and sizing data was provided for configurations along with UAVs designed by authors. Also, phenomena such as tail strike and overturn were explained with resultant parameters. 

An Evaluation on Landing Gear Configurations of Fixed-Wing, Rotary-Wing, and Hybrid UAVs

Design and development of a novel fixed-wing biplane micro air vehicle with enhanced static stability

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Design and development of a novel fixed-wing biplane micro air vehicle with enhanced static stability